# TCDS E00049EN: General Electric Company GE Aviation

- Type: Type certificate data sheet
- Status: Current
- Holder: General Electric Company GE Aviation
- Revision: 21
- Revised: June 11, 2024
- Product: Engine
- Certification basis: Part 33
- Registered aircraft: 166, by the registry models matched to it (OpenAirDocs)
- Data sheet PDF: https://openairdocs.org/files/sha256/80/02/80022b58017c13111df3b90b33253e69cf009c921b11b3b6245ce2b452dc67f0
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/DRSDOCID178969540120240613141736.0001
- Page: https://openairdocs.org/tcds/E00049EN

## Models (8)

As the data sheet lists them.

- GE90-113B
- GE90-110B1
- GE90-76B
- GE90-77B
- GE90-90B
- GE90-115B
- GE90-94B
- GE90-85B

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Engines of models described herein conforming with this data sheet (which is part of Type Certificate Number E00049EN) and other 
approved data on file with the Federal Aviation Administration, meet the minimum standards for use in certificated aircraft in accordance 
with pertinent aircraft data sheets and applicable portions of the Federal Aviation Regulations, provided they are installed, operated, and 
maintained as prescribed by the approved manufacturer's manuals and other approved instructions. 
 
TYPE CERTIFICATE (TC) HOLDER:  General  Electric Company 
GE Aviation 
1 Neumann Way 
Cincinnati, OH 45215-6310 
 
I. MODELS GE90-76B GE90-77B GE90-85B GE90-90B 
TYPE Dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure compressor is 
driven by a 2-stage high pressure turbine. The single stage fan and 3-stage low pressure 
compressor are driven by a 6-stage low pressure turbine. 
RATINGS (See NOTE 5) 
Maximum continuous at sea 
level, static thrust, lb 
Takeoff (5 min. see NOTE 16) at sea 
level, static thrust, lb 
Flat rating ambient temperature 
Takeoff 
Maximum continuous 
 
75,430 
 
81,070 
 
 
91ºF/32.8ºC 
77ºF/25ºC 
 
75,430 
 
81,700 
 
 
- - 
- - 
 
81,230 
 
88,870 
 
 
86ºF/30ºC 
- - 
 
90,580 
 
94,000 
 
 
- - 
- - 
COMPONENTS (GE P/Ns) 
Hydromechanical Control Unit 
 
 
Full Authority Digital Engine Control (FADEC) 
Hardware (H/W) & Software (S/W) 
H/W (See NOTE 21) 
 
 
S/W (See NOTE 21) 
 
1693M75 
1851M65 
 
 
1838M16 
1959M87 
1838M16 
 
1853M99 
 
- - 
- - 
 
 
- - - 
- - 
- - 
 
- - 
 
- - 
- - 
 
 
- - - 
- - 
- - 
 
- - 
 
- - 
- - 
 
 
- - - 
- - 
- - 
 
- - 
 
 
 
 
 
 
 
* 
PAGE 1 2 3 4 5 6 7 8 9 10 11 12 
REV. 21 9 18 19 21 18 18 18 18 18 18 21 
 LEGEND: "- -" INDICATES "SAME AS PRECEDING MODEL" 
"- - -" NOT APPLICABLE 
NOTE: SIGNIFICANT CHANGES ARE BLACK-LINED IN THE 
LEFT MARGIN. 
 
 
 
U.S. DEPARTMENT OF TRANSPORTATION 
FEDERAL AVIATION ADMINISTRATION 
TYPE CERTIFICATE DATA SHEET E00049EN 
TCDS NUMBER E00049EN 
REVISION 21 
DATE: June 11, 2024 
 
GENERAL ELECTRIC COMPANY 
MODELS: 
GE90-76B GE90-90B GE90 -113B 
GE90-77B GE90-94B GE90 -115B 
GE90-85B GE90-110B1

TCDS E00049EN Page 2 of 12 
 
 
I. MODELS (cont.) GE90-76B GE90-77B GE90-85B GE90-90B 
Configuration Type Box (See NOTE 10) 
 
 
 
 
 
 
 
 
FADEC Rating Plug 
 
Main Fuel Pump 
IGNITION SYSTEM 
Two ignition units GE P/N 
Two ignitor plugs GE P/N 
320-837-701-0 
320-839-501-0 
320-892-101-0 
320-892-201-0 
320-846-701-0 
320-892-601-0 
320-915-201-0 
320-921-501-0 
 
320-833-701-0 
 
 
1689M10 
 
9238M66 
1754M84 
- - - 
- - 
- - - 
- - 
- - 
- - 
- - 
- - 
 
320-833-901-0 
 
 
- - 
 
- - 
- - 
- - - 
- - 
- - - 
- - 
- - 
- - 
- - 
- - 
 
320-833-801-0 
320-834-201-0 
 
- - 
 
- - 
- - 
- - - 
- - 
- - - 
- - 
- - 
- - 
- - 
- - 
 
320-834-001-0 
 
 
- - 
 
- - 
- - 
 
PRINCIPAL DIMENSIONS (in) 
 
Length (Fan spinner to nozzle 
centerbody) 
Width (maximum envelope) 
Height (maximum envelope) 
 
 
286.9 
152.4 
155.6 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
WEIGHT (DRY) 
Includes basic engine, basic 
engine accessories, and 
optional equipment as listed 
in the manufacturer's engine 
specifications. 
17,400 - - - - - - 
CENTER OF GRAVITY LOCATIONS (in) 
(Engine only) 
 
Station (axial) 
Waterline 
Buttline 
 
 
227.5+1.5 
99.9+0.5 
100.4+0.5 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- - 
 
 
- - 
- - 
- -

TCDS E00049EN Page 3 of 12 
 
 
II. MODELS GE90-94B    
TYPE Dual rotor, axial flow, high bypass ratio turbofan. The 10-stage high pressure 
compressor is driven by a 2-stage high pressure turbine. The single stage fan and 
3-stage low pressure compressor are driven by a 6-stage low pressure turbine. 
RATINGS (See NOTE 5) 
 
Maximum continuous at sea 
level, static thrust, lb 
Takeoff (5 min. see NOTE 16) at sea 
level, static thrust, lb 
Flat rating ambient temperature 
Takeoff 
Maximum continuous 
 
 
90,580 
 
97,300 
 
86oF/30ºC 
77oF/25ºC 
   
COMPONENTS (GE P/Ns) 
Hydro-mechanical Control Unit 
 
 
Full Authority Digital Engine Control (FADEC) 
Hardware (H/W) & Software (S/W) 
 
Hardware (H/W) (See NOTE 21) 
Software (S/W) (See NOTE 21) 
Configuration Type Box (See NOTE 10) 
FADEC Rating Plug 
Main Fuel Pump 
 
IGNITION SYSTEM 
Two ignition units GE P/N 
Two ignitor plugs GE P/N 
 
1851M65 
 
 
 
1959M87 
 
1838M16 
 
1853M99 
320-921-501-0 
 
320-834-301-0 
 
1689M10 
 
 
9238M66 
1754M84 
   
PRINCIPAL DIMENSIONS (in) 
 
Length (Fan spinner to nozzle 
centerbody) 
Width (maximum envelope) 
Height (maximum envelope) 
 
286.9 
 
152.4 
155.6 
   
WEIGHT (DRY) 
Includes basic engine, basic 
engine accessories, and 
optional equipment as listed 
in the manufacturer's engine 
specifications. 
17,400 
   
CENTER OF GRAVITY LOCATIONS (in) 
(Engine only) 
Station (axial) 
Waterline 
Buttline 
 
 
227.5+1.5 
99.9+0.5 
100.4+0.5

TCDS E00049EN Page 4 of 12 
 
 
III MODELS GE90-110B1 GE90-113B GE90-115B  
TYPE 
RATINGS (See NOTE 5) 
 
Maximum continuous at sea 
level, static thrust, lb 
Takeoff (5 min. see NOTE 16) at sea 
level, static thrust, lb 
 
Flat rating ambient temperature 
Takeoff 
Maximum continuous 
 
COMPONENTS (GE P/Ns) 
Hydro-mechanical Control Unit 
 
Full Authority Digital Engine Control (FADEC) 
Hardware (H/W) (See NOTE 21) 
 
Software (S/W) (See NOTE 21 
Configuration Type Box 
 
 
FADEC Rating Plug  G01 
G02 
G03 
G04 
Main Fuel Pump 
 
IGNITION SYSTEM 
Two ignition units GE P/N 
Two ignitor plugs GE P/N 
 
 
110,000 
 
110,760 
 
 
 
92ºF/33ºC 
77ºF/25ºC 
 
 
110,000 
 
113,530 
 
 
86ºF/30ºC 
77ºF/25ºC 
 
 
110,000 
 
115,540 
 
 
86ºF/30ºC 
77ºF/25ºC 
 
1962M80 
 
1962M67 
 
2041M27 
 
390-850-001-0 
390-851-001-0 
390-850-002-0 
390-851-002-0 
390-801-011-0 
390-803-001-0 
390-803-011-0 
390-803-021-0 
2042M69 
 
 
9238M66 
1754M84 
 
- - 
 
- - 
 
- - 
 
- - 
- - 
- - 
- - 
390-802-001-0 
390-804-001-0 
- - 
- - 
- - 
 
 
- - 
 
- - 
 
- - 
 
- - 
 
- - 
 
- - 
- - 
- - 
- - 
390-800-001-0 
390-805-001-0 
390-805-011-0 
390-805-021-0 
- - 
 
 
- - 
 
- - 
 
PRINCIPAL DIMENSION (in) 
 
Length (Fan spinner to nozzle 
centerbody) 
Width (maximum envelope) 
Height (maximum envelope) 
286.67 
 
148.38 
154.56 
- - 
 
- - 
- - 
- - 
 
- - 
- - 
WEIGHT (DRY) 
Includes basic engine, basic 
engine accessories, and 
optional equipment as listed 
in the manufacturer’s engine 
specifications. 
19316 - - - - 
CENTER OF GRAVITY LOCATIONS (in) 
(Engine only) 
Station (axial) 
Waterline 
Buttline 
 
219.2+1.5 
100.14+0.5 
100.28+0.5 
 
- - 
- - 
- - 
 
- - 
- - 
- -

TCDS E00049EN Page 5 of 12 
 
 
IV. MODELS ALL 
FUEL See NOTE 7 for approved fuels. 
OIL Type 2 oils conforming to GE90 Specification D50TF1 or the latest revisions are 
authorized. For approved brand of oils refer to GE90 Service Bulletin 79-001. 
 
CERTIFICATION BASIS 
(-76B/-77B/-85B/-90B) 
 
 
 
CERTIFICATION BASIS 
(-94B) 
 
 
 
 
 
 
 
CERTIFICATION BASIS 
(-113B) 
 
 
 
 
 
 
 
 
CERTIFICATION BASIS 
(-110B1, -115B) 
 
Title 14, Code of Federal Regulations (14 CFR) part 33, effective February 1, 
1965, amendments 33-1 through 33-15, inclusive; 14 CFR part 34, amendment 4, 
effective June 29, 2009; and Special Condition Number SC-33-ANE-08-NE; and 
para. 33.71(c)(4), amendment 33-27, effective November 24, 2008. 
 
14 CFR part 33, effective February 1, 1965, including amendments 33-1 through 
33-15, and amendment 33-19; 14 CFR part 34, amendment 5, effective December 
31, 2012; Special Condition SC-33-ANE-08-NE, and Equivalent Level of Safety 
Finding for §33.68(b) Number 8040-ELOS-00-NE-01; and para. 33.71(c)(4), 
amendment 33-27, effective November 24, 2008. 
See NOTE 25 for detailed summary of the certification basis for fuel venting and 
exhaust emissions for GE90-94B model. 
 
14 CFR part 33, effective February 1, 1965, including Amendments 33-1 through 
33-20; 14 CFR part 34, amendment 5, effective December 31, 2012; Special 
Condition SC-33-ANE-08-NE, and Exemption to §33.73(b), No. 7953 dated 
January 15, 2003; and para. 33.71(c)(4), amendment 33-27, effective November 
24, 2008, Part 33.27(c)(2)(v) ELOS # GE90-2015-MT-07-P-1 dated July 6, 2016, 
Part 33.27(c) ELOS # GE90-2016-MT-03-P2 dated November 30, 2016. 
 
See NOTE 25 for detailed summary of the certification basis for fuel venting and 
exhaust emissions for GE90-113B model. 
 
14 CFR part 33, effective February 1, 1965, including Amendments 33-1 through 
33-20; 14 CFR part 34, amendment 7A, effective May 24, 2024; Special 
Condition SC-33-ANE-08-NE, and Exemption to §33.73(b), No. 7953 dated 
January 15, 2003; and para. 33.71(c)(4), amendment 33-27, effective November 
24, 2008, Part 33.27(c)(2)(v) ELOS # GE90-2015-MT-07-P-1 dated July 6, 2016, 
Part 33.27(c) ELOS # GE90-2016-MT-03-P2 dated November 30, 2016. 
 
See NOTE 25 for detailed summary of the certification basis for fuel venting and 
exhaust emissions for GE90-110B1 and GE90-115B models. 
 
 
TYPE CERTIFICATE E00049EN 
MODELS APPLICATION DATE ISSUED/AMENDED 
GE90-76B  DEC 16, 1991  FEB 2, 1995 
GE90-85B DEC 16, 1991 FEB 2, 1995 
GE90-90B AUG 10, 1994 JUL 2, 1996 
GE90-77B NOV 20, 1995 JUL 2, 1996 
GE90-94B MAR 5, 1999 JUN 9, 2000 
GE90-113B JUN 27, 2000 JUL 30, 2003 
GE90-115B JUN 27, 2000 JUL 30, 2003 
GE90-110B1 JAN 9, 2002 JUL 30, 2003 
 
GE90-75B DEC 16, 1991 FEB 2, 1995 
(Deleted JUL 24, 1995) 
GE90-92B AUG 10, 1994 JUL 2, 1996 
(Deleted June 26, 2000) 
PRODUCTION BASIS GE90-76B/-77B/-85B/-90B/-94B/-110B1/-113B/-115B Production Certificate No. 
108

TCDS E00049EN Page 6 of 12 
 
 
 NOTES 
NOTE 1. MAXIMUM PERMISSIBLE ENGINE 
ROTOR SPEEDS GE90-76B GE90-77B/-85B/-90B/-94B GE90-110B1/-113B/-115B 
 
Low pressure rotor (N1) 2,465 RPM 2,465 RPM 2,602 RPM 
(109.0%)* (109.0%)* (110.5%)*** 
High pressure rotor (N2) 10,705 RPM 10,918 RPM 11,292 RPM 
(114.7%)** (117%)** (121%)** 
* 100% N1 is 2,261.5 RPM 
** 100% N2 is 9,332.0 RPM 
*** 100% N1 is 2,355.0 RPM 
NOTE 2. MAXIMUM PERMISSIBLE TEMPERATURES 
Indicated turbine exhaust 
gas temperature (T49) GE90-76B GE90-77B/-85B/-90B/-94B 
(see NOTE 10) 
Takeoff (5 minute; see NOTE 16)  1,787ºF (975ºC)*  1,885ºF (1030ºC) 
Maximum Continuous 1,697ºF (925ºC) 1,859ºF (1015ºC) 
Ground starts (manual or auto) 1,382ºF (750ºC) 1,382ºF (750ºC)** 
Inflight starts (manual or auto) 1,517ºF (825ºC) - - 
 
* 60 seconds maximum transient 1,796ºF (980ºC) - - - 
** 40 seconds start EGT exceedance 1,517ºF (825ºC) 
limit for –94B only 
 
Oil temperature limits 
Continuous 255ºF (124ºC) - - 
Transient 275ºF (135ºC) - - 
 
 
Indicated turbine exhaust 
gas temperature (T49) GE90-110B1/ -113B/ -115B 
 
Takeoff (5 minute; see NOTE 16) 1,994ºF (1,090ºC)*** 
Maximum Continuous 1,922ºF (1,050ºC) 
Ground starts (manual or auto) 1,382ºF (750ºC) 
Inflight starts (manual or auto) 1,517ºF (825ºC) 
 
***30 seconds maximum transient 2,003ºF (1,095ºC) 
 
Oil temperature limits 
Continuous 270ºF (132ºC) 
Transient 290ºF (143ºC)

TCDS E00049EN Page 7 of 12 
 
 
NOTE 3. FUEL AND OIL PRESSURE LIMITS 
 
FUEL PRESSURE LIMITS AT THE ENGINE PUMP INLET 
Maximum allowable fuel pressure is 70 psig. Minimum allowable fuel pressure under normal operating conditions (fully 
operational aircraft fuel system) is 5.0 psia. At altitudes of 38,000 feet and below, transitory excursions of 15 seconds or less 
to a minimum fuel pressure of 3.5 psia are allowable provided the average fuel pressure remains above 4.5 psia. 
 
OIL PRESSURE LIMITS 
LOW PRESSURE 
The limit is 10.0 psid (69 kPa diff.). (See NOTE 14) 
 
NOTE 4. ACCESSORY DRIVE PROVISIONS 
GE90-76B/-77B/-85B/-90B/-94B 
 
 
 
DRIVE PAD 
 
Rotation 
Facing 
Gearbox Pad 
 
Gear Ratio 
To 
Core Speed 
 
Horsepower 
Continuous 
Pad Rating 
HP (kW) 
 
Shear 
Torque 
in-lb (N-m) 
 
Maximum 
Overhung 
Moment 
in-lb (N-m) 
IDG (120 kVA) CCW (*) 0.7947 243 (181.3) 10,000 – 10,500 2,000 (226.0) 
    (1,130 – 1,187)  
Hydraulic Pump CCW 0.3783 85 (63.5) 4,250 – 4,850 230 (26.0) 
    (480 - 548)  
VSCF/PMG CCW 2.4126 58 (43.3) 3,500; 4,500** 400 (45.2) 
Generator    (395, 508)**  
(20/30 kVA)      
IDG Overload 
Limits 
304 HP (226.8 kVA) for 5 minutes per 1,000 hours of operation 
406 HP (302.9 kVA) for 5 seconds per 1,000 hours of operation 
500 HP (373.0 kVA) electrical fault 
 
VSCF/PMG 
Overload limits 
87 HP (64.9 kVA) for 5 minutes per 1,000 hours of operation 
116 HP (86.5 kVA) for 5 seconds per 1,000 hours of operation 
128 HP (95.5 kVA) electrical fault 
 100% core speed is 9,332 RPM 
(*) Counter Clockwise 
(**) Shear torque capability is a function of operator requirements. Consult GE Aviation for 
installed capability.

TCDS E00049EN Page 8 of 12 
 
NOTE 4. Cont. 
GE90-110B1/-113B/-115B 
 
 
 
 
DRIVE PAD 
 
Rotation 
Facing 
Gearbox Pad 
 
Gear Ratio 
To 
Core Speed 
 
Horsepower 
Continuous 
Pad Rating 
HP (kW) 
 
Shear 
Torque 
in-lb (N-m) 
 
Maximum 
Overhung 
Moment 
in-lb (N-m) 
IDG (120 kVA) CCW (*) 0.7947 243 (181.3) 10,500 max 2,000 (226.0) 
    (1,187 max)  
Hydraulic Pump CCW 0.3783 85 (63.5) 4,250 – 4,850 230 (26.0) 
    (480 - 548)  
VSCF/PMG CCW 2.4126 58 (43.3) 1,250 max 400 (45.2) 
Generator    (141.2 max)  
(20/30 kVA)      
IDG Overload 
Limits 
304 HP (226.8 kVA) for 5 minutes per 1,000 hours of operation 
406 HP (302.9 kVA) for 5 seconds per 1,000 hours of operation 
500 HP (373.0 kVA) electrical fault 
VSCF/PMG 
Overload limits 
 
87 HP (64.9 kVA) for 5 minutes per 1,000 hours of operation 
116 HP (86.5 kVA) for 5 seconds per 1,000 hours of operation 
128 HP (95.5 kVA) electrical fault 
 100% core speed is 9,332 RPM 
(*) Counter Clockwise 
 
NOTE 5. Engine ratings are based on calibrated test stand performance under the following conditions: 
1. Sea level static, standard pressure (14.696 psia), 59°F 
2. No customer bleed or customer horsepower extraction 
3. Ideal inlet, 100% ram recovery 
4. Production aircraft flight cowling 
5. Production instrumentation 
6. Fuel lower heating value of 18,400 BTU# 
 
NOTE 6. MAXIMUM PERMISSIBLE AIR BLEED EXTRACTION 
 
Allowable Bleed Limits (%) 
GE90-76B/-77B/-85B/-90B/-94B 
 
Below 23% N1K 
23 to 31% N1K 
31 to 57.4% N1K 
57.4 to 80% N1K 
80 to 96.8% N1K 
Above 96.8% N1K 
Stage 4 S tage 7 Stage 10 Maximum 
Allowable 
7.8 1.8 13.6 15.4 
7.6 1.6 12.8 14.4 
7.4 1.3 12.6 13.9 
7.2 1.3 12.6 13.9 
7.0 1.3 6.5 8.3 
6.5 1.3 6.5 7.8

TCDS E00049EN Page 9 of 12 
 
NOTE 6. Cont. 
 
GE90-110B1/-113B/-115B Stage 4 Stage 7 Stage 9 Maximum 
Allowable 
Below 27% N1K 
At 51% N1K 
At 80% N1K 
At 88% N1K 
At 93% N1K today 
Above 93% N1K 
7.6 
7.6 
7.6 
7.6 
7.6 
7.6 
1.5 
1.5 
1.5 
1.5 
1.5 
1.5 
11.2 
11.5 
12.0 
11.0 
8.0 
7.3 
12.7 
13.0 
13.5 
12.5 
9.1 
9.1 
 
NOTE 7. FUEL 
Approved fuels must conform to GE Specification D50TF2. Certain fuels such as those produced to PRC 
Specification RP3 meet the requirements of D50TF2 by means of the Specification. The engine will operate with a 
mixture of fuels or additives conforming to GE Specification D50TF2. 
NOTE 8. Life limits established for critical rotating components for: 
GE90-76B/-77B/-85B/-90B/-94B are published in Chapter 5 of the GE90 Engine Manual, GEK 100700 
GE90-110B1/-113B/-115B are published in Chapter 5 of the GE90-100 Engine Manual, GEK 109993 
NOTE 9. Power setting, power checks, and control of engine thrust output in all operations are based on Fan Speed (N1). Speed 
sensors are included in the engine assembly for this purpose. 
NOTE 10. GE90-76B engines with configuration type box number 320-839-501-0 must incorporate the HP/LP turbine hardware 
and associated changes per General Electric GE90 Service Bulletin 72-169. The FADEC incorporates a 30ºC shunt. 
The corresponding indicated EGT limits are 975ºC (take-off), 980ºC (take-off with 60 second max. transient), and 
965ºC (max. continuous). 
NOTE 11. For ground operation in icing conditions the following procedures must be observed: 
 
GE90-76B/-77B/-85B/-90B/-94B 
During ground operations (including taxi-in and taxi-out) in icing conditions, the pilot must perform one of the 
following shed procedures: 
(a) Run up the engines momentarily to a minimum of 50% N1 at intervals not to exceed 15 minutes, or 
(b) For operation at ambient conditions of -6 ºC (23 ºF) and above, and at airport altitudes up to 3,048 meters (10,000 
ft), perform the following at intervals not to exceed 60 minutes: 
1) Increase throttle to a minimum of 55% N1 
2) Dwell at the specified N1 for 20 seconds minimum 
3) Decelerate to idle or proceed with normal takeoff procedure. 
See GE90 Operating Instructions Manual GEK 100703. 
 
GE90-110B1/-113B/-115B 
During ground operations (including taxi-in and taxi-out) in icing conditions, the engine must be run up momentarily 
to a minimum of 50% N1 at intervals not to exceed 60 minutes. See GE90-100 Operating Instructions Manual 
GEK109994. Note: For possible variations in engine acceleration times in icing conditions see the GE90-100 
Installation Manual GEK 109995.

TCDS E00049EN Page 10 of 12 
 
 
NOTE 12. All GE90 engines with configuration type box part numbers 320-892-101-0 or 320-892-201-0 must incorporate the 
PT25 extended wedge ice shield per GE90 Service Bulletin 77-008 and must incorporate FADEC software P/N 
1853M99P06 (version 9.1.9.7 or later) per GE90 Service Bulletin 73-040. 
 
All GE90 engines with configuration type box part numbers 320-837-701-0, 320-839-501-0, 320-892-101-0, 320-892- 
201-0, 320-846-701-0, 320-892-601-0 and 320-915-201-0, have a minimum permissible N2 of 6,066 RPM for in- 
flight operation during icing conditions. 
 
All GE90 engines with configuration type box part numbers 320-921-501-0 have a minimum permissible N2 of 6,310 
RPM for in-flight operation during icing conditions. 
 
All GE90 engines with configuration type box part numbers 390-850-001-0 and 390-851-001-0 have a minimum 
permissible N1 of 730 RPM for in-flight operation during icing conditions. 
NOTE 13. Demonstration of compliance to §33.68, Induction System Icing is installation specific to the B777-200LR/300ER and 
B777 Freighter airplanes for the GE90-110B1/-113B/-115B model engines. Installation of these model engines on 
different airplane models or types will require a separate evaluation and finding of compliance to §33.68. 
NOTE 14. During "negative-G" operation only, it is permissible to operate below minimum oil pressure of 10 psid (69.0 kPa diff) 
for a maximum of 15 seconds. 
See GE90 Operating Instructions Manual, GEK 100703, for GE90-76B/-77B/-85B/-90B/-94B 
See GE90-100 Operating Instructions Manual, GEK 109994, for GE90-110B1/-113B/-115B. 
NOTE 15. THESE MODELS INCORPORATE THE FOLLOWING GENERAL CHARACTERISTICS 
 
ENGINE MODEL CHARACTERISTICS 
GE90-76B Basic Model 
GE90-77B Same as GE90-76B except improved HPT/LPT flowpath and higher 
thrust ratings. Corresponding Rating Plug changes. 
GE90-85B Same as GE90-76B except higher thrust ratings. Corresponding 
Rating Plug changes. 
GE90-90B Same as GE90-77B except higher thrust ratings. Corresponding 
Rating Plug changes. 
GE90-94B Same as GE90-90B except 3D aero HPC and higher thrust ratings. 
Corresponding rating plug changes. 
GE90-110B1 Differs primarily from basic model in FAN, LPC, HPC, HPT and LPT hardware, 
higher takeoff thrust rating with increased speed, and temperature limitations. Corresponding rating plug changes. See 
NOTE 22. 
GE90-113B Same as GE90-110B1 except higher thrust ratings. Corresponding 
Rating Plug changes. 
GE90-115B Same as GE90-113B except higher thrust ratings. Corresponding 
Rating Plug changes.

TCDS E00049EN Page 11 of 12 
 
 
NOTE 16. The normal 5 minute takeoff time limit may be extended to 10 minutes for engine out contingency. 
NOTE 17. TIME LIMITED DISPATCH CRITERIA 
 
Criteria pertaining to the dispatch and maintenance requirements for the engine control systems are specified in: 
For the GE90-76B/-77B/-85B/-90B/-94B see General Electric Document GEK 103084 and the Airworthiness 
Limitations Section of the GE90 Engine Manual GEK 100700, which defines the various configurations and 
maximum operating intervals. 
 
For the GE90-110B1/-113B/-115B the requirements are defined in the Airworthiness Limitations section of the GE90- 
100 Engine Manual GEK 109993 
NOTE 18. For approval of repairs of fan blade composite material in the root section of the fan blade up to the inner annulus flow 
path line see the Airworthiness Limitations Section of GE90 Engine Manual GEK 100700 for the GE90-76B/-77B/- 
85B/-90B/-94B and GE90-100 Engine Manual GEK 109993 for the GE90-110B1/-113B/-115B. 
NOTE 19. Note deleted. 
NOTE 20. Reserved. 
NOTE 21. The FADEC unit P/N originally defined both hardware and software. The hardware and software are now defined by 
separate P/Ns. The engine should be equipped with a FADEC defined either by the combined P/N or by the hardware 
and the software P/Ns. 
NOTE 22. 
 
 
 
 
 
 
 
 
 
 
 
 
NOTE 23. 
An exemption to §21.19(a) was granted and issued in Washington, DC, on August 26, 2002, for the GE90-110B1/- 
113B/-115B engine models. This exemption allowed GEAE to amend Type Certificate No. E00049EN to add these 
models rather than apply for a new type certificate for those engines, subject to the following conditions and 
limitations: 
1. GEAE must comply with §21.17 as if it was a new type certificate. 
2. GEAE must conduct a large flocking bird test as part of compliance with §33.76, Bird Ingestion. 
3. GEAE must include an engine test to demonstrate compliance to §33.90, Initial Maintenance Inspection. 
4. An applicant installing the GE90-110B1/-113B/-115B engine models into an aircraft must comply with 
all of the applicable airworthiness standards for a new type certificated engine, including applicable aircraft 
special conditions. 
 
Demonstration of compliance to §33.73(b) Power or Thrust Response is installation specific to the B777- 
200LR/300ER and B777 Freighter airplanes for the GE90-110B1/-113B/-115B model engines. Installation of these 
model engines on different airplane models or types will require a separate evaluation and finding of compliance to 
§33.73(b). 
NOTE 24. The engine oil tank filler cap of GE90-76B/-77B/-85B/-90B/-94B and GE90-110B1/-113B/-115B engine model meet 
the requirement of §33.71(c)(4).

TCDS E00049EN Page 12 of 12 
 
 
NOTE 25. The following emissions standards promulgated in 14 CFR Part 34, Amendment 5, effective December 31, 2012, and 
40 CFR Part 87, effective July 18, 2012, have been complied with for: GE90-94B and GE90-113B. 
Fuel Venting Emission Standards: 14 CFR 34.10(a) and 34.11; in addition, 40 CFR 87.10(a) and 87.11. Smoke 
Number (SN) Emission Standards: 14 CFR 34.21(e)(2); in addition, 40 CFR 87.23(c)(1). 
Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 87.23(c)(l). Hydrocarbons 
(HC) Emission Standards: 14 CFR 34.21(d)(l)(i); in addition, 40 CFR 87.23(c)(l). 
Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(a)(2); in addition, 40 CFR 87.23(c)(2). 
In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the 
engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Third 
Edition, Part III, Chapter 2, Section 2.2.2 for SN, Section 2.3.2 for CO and HC, Section 2.3.2 .d.3 for NOx (also 
known as CAEP/6), and Part II Chapter 2 for fuel venting have also been demonstrated. 
 
The following emissions standards promulgated in 14 CFR part 34, amendment 7A, effective May 24, 2024, and 40 
CFR part 1031, effective December 23, 2022, have been complied with for: GE90-110B1 and GE90-115B. 
 
Fuel Venting Emission Standards: 14 CFR 34.11; in addition, 40 CFR 1031.30(b) 
 
Smoke Number (SN) Emission Standards: 14 CFR 34.21(e); in addition, 40 CFR 1031.60(a)(5) 
 
Hydrocarbons (HC) Emission Standards: 14 CFR 34.21(d)(1)(i); in addition, 40 CFR 1031.60(c) 
 
Carbon Monoxide (CO) Emission Standards: 14 CFR 34.21(d)(1)(ii); in addition, 40 CFR 1031.60(d) 
 
Oxides of Nitrogen (NOx) Emission Standards: 14 CFR 34.23(a)(2); in addition, 40 CFR 1031.60(e)(4) (also known 
as Tier 6 in-production) 
 
non-volatile Particulate Matter (nvPM) Mass Concentration Emission Standards: 14 CFR 34.25(a)(1); in addition, 40 
CFR 1031.60(a)(6) (also known as Tier 10) 
 
nvPM Mass and Number Emission Standards: 14 CFR 34.25(a)(2); in addition, 40 CFR 1031.60(b)(2) (also known as 
Tier 11 in-production) 
In addition to the FAA's finding of compliance based on the certification requirements defined in this TCDS, the 
engine manufacturer has declared that the ICAO emissions standards identified in Annex 16, Volume II, Fourth 
Edition, Amendment 10, effective July 20, 2020, have also been demonstrated for the following: 
• Part II, Chapter 2 for Fuel Venting 
• Part III, Chapter 2, Section 2.2.2 for Smoke number, 
• Part III, Chapter 2, Section 2.3.2 for Carbon monoxide and Hydrocarbons, 
• Part III, Chapter 2, Section 2.3.2.d for Oxides of Nitrogen (also known as CAEP/6), 
• Part III, Chapter 4, Section 4.2.2.1 for nvPM Mass Concentration (also known as CAEP/10), and  
• Part III, Chapter 4, Section 4.2.2.2 for nvPM Mass and Number (also known as CAEP/11) 
 
 
-- END --
```

## ADs (48, in force first)

- [AD 2025-25-07](https://openairdocs.org/ad/2025-25-07): Turbine Section · General Electric Company GE GE90-90B, GE90-94B, GE90-110B1 and 1 more. Effective Feb 6, 2026
- [AD 2025-07-10](https://openairdocs.org/ad/2025-07-10): Fuel Controlling System · General Electric Company GE GE90-110B1 and GE90-115B. Effective May 21, 2025
- [AD 2024-06-15](https://openairdocs.org/ad/2024-06-15): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective May 14, 2024
- [AD 2023-26-07](https://openairdocs.org/ad/2023-26-07): Turbine Section · General Electric GE90-90B, GE90-94B, GE90-110B1 and 1 more. Effective Feb 27, 2024
- [AD 2023-05-17](https://openairdocs.org/ad/2023-05-17): Turbine Section · General Electric GE90-76B, GE90-85B, GE90-90B and 1 more. Effective May 10, 2023
- [AD 2023-04-19](https://openairdocs.org/ad/2023-04-19): Turbine Engine Compressor Section · General Electric GE90-110B1 and GE90-115B. Effective Mar 27, 2023
- [AD 2022-23-09](https://openairdocs.org/ad/2022-23-09): Turbine Engine Compressor Section, Turbine Section · General Electric GE90-90B, GE90-94B, GE90-110B1 and 1 more. Effective Jan 17, 2023
- [AD 2022-18-06](https://openairdocs.org/ad/2022-18-06): Turbine Engine Compressor Section, Turbine Section · General Electric GE90-110B1, GE90-115B, GE90-76B and 3 more. Effective Oct 26, 2022
- [AD 2021-26-06](https://openairdocs.org/ad/2021-26-06): Turbine Engine Accessory Drive · General Electric GE90-76B, GE90-85B, GE90-90B and 3 more. Effective Feb 15, 2022
- [AD 2020-21-13](https://openairdocs.org/ad/2020-21-13): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective Nov 17, 2020
- [AD 2020-18-14](https://openairdocs.org/ad/2020-18-14): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective Oct 21, 2020
- [AD 2020-10-04](https://openairdocs.org/ad/2020-10-04): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective May 27, 2020
- [AD 2020-01-55](https://openairdocs.org/ad/2020-01-55): Turbine Section · General Electric GE90-110B1 and GE90-115B. Effective Mar 2, 2020
- [AD 2019-21-51](https://openairdocs.org/ad/2019-21-51): Turbine Section · General Electric GE90-115B. Effective Dec 6, 2019
- [AD 2018-20-23](https://openairdocs.org/ad/2018-20-23): Turbine Engine Compressor Section · General Electric GE90-110B1 and GE90-115B. Effective Nov 30, 2018
- [AD 2018-20-22](https://openairdocs.org/ad/2018-20-22): Turbine Section · General Electric GE90-110B1, GE90-113B and GE90-115B. Effective Nov 13, 2018
- [AD 2018-17-12](https://openairdocs.org/ad/2018-17-12): Turbine Engine Compressor Section · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Sep 24, 2018
- [AD 2017-08-06](https://openairdocs.org/ad/2017-08-06): Engine Oil Cooler · General Electric GE90-110B1, GE90-115B, GE90-76B and 3 more. Effective May 22, 2017
- [AD 2017-08-05](https://openairdocs.org/ad/2017-08-05): Engine Compressor Section · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective May 19, 2017
- [AD 2016-19-09](https://openairdocs.org/ad/2016-19-09): High-pressure compressor (HPC) · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Nov 4, 2016
- [AD 2015-27-01](https://openairdocs.org/ad/2015-27-01): High-pressure compressor (HPC) stage 8-10 spool · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Jan 27, 2016
- [AD 2013-23-18](https://openairdocs.org/ad/2013-23-18): Variable bypass valve (VBV) actuator fuel supply tube · General Electric GE90-110B1 and GE90-115B. Effective Jan 7, 2014
- [AD 2013-17-07](https://openairdocs.org/ad/2013-17-07): Stage 1 high-pressure turbine (HPT) stator shrouds · General Electric GE90-110B1, GE90-115B, GE90-76B and 3 more. Effective Oct 18, 2013
- [AD 2013-15-20](https://openairdocs.org/ad/2013-15-20): Transfer gearbox assembly (TGB) radial gearshafts · General Electric GE90-110B1, GE90-113B, GE90-115B and 5 more. Effective Aug 21, 2013
- [AD 2011-26-11](https://openairdocs.org/ad/2011-26-11): HPC stages 1-2 seal teeth · General Electric GE90-110B1 and GE90-115B. Effective Feb 3, 2012
- [AD 2011-15-06](https://openairdocs.org/ad/2011-15-06): High-pressure compressor rotor (HPCR) · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Aug 18, 2011
- [AD 2009-25-14](https://openairdocs.org/ad/2009-25-14): Blade · General Electric GE90-110B1, GE90-113B and GE90-115B. Effective Jan 19, 2010
- [AD 2007-10-05](https://openairdocs.org/ad/2007-10-05): Turbine Center Frames (TCFs) · General Electric GE90-110B1, GE90-113B and GE90-115B. Effective Jun 14, 2007
- [AD 2002-04-11](https://openairdocs.org/ad/2002-04-11): Life Limits Section of Instructions for Continued Airworthiness (ICA) · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Apr 8, 2002
- [AD 2002-01-12](https://openairdocs.org/ad/2002-01-12): High Pressure Turbine (HPT) Interstage Seal · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Feb 26, 2002
- [AD 2002-01-27](https://openairdocs.org/ad/2002-01-27): High Pressure Compressor Stage 2-6 Spool · General Electric GE90-76B, GE90-77B, GE90-85B and 1 more. Effective Feb 14, 2002
- [AD 2001-21-03](https://openairdocs.org/ad/2001-21-03): P3B and Ps3 Sense Lines · General Electric GE90-76B, GE90-77B, GE90-85B and 1 more. Effective Nov 26, 2001
- [AD 2000-03-02](https://openairdocs.org/ad/2000-03-02): General Electric GE90-76B, GE90-85B and GE90-90B. Effective Apr 7, 2000
- [AD 2000-05-10](https://openairdocs.org/ad/2000-05-10): General Electric GE90-85B. Effective Apr 7, 2000
- [AD 98-09-15](https://openairdocs.org/ad/98-09-15): Rotating Components · General Electric GE90-76B. Effective Jul 6, 1998
- [AD 97-12-04](https://openairdocs.org/ad/97-12-04): Liberated CDP Manifold Material · General Electric Aircraft Engines GE90-92B, GE90-76B, GE90-77B and 2 more. Effective Jun 27, 1997
- [AD 97-12-05](https://openairdocs.org/ad/97-12-05): (VSCF) Gearshaft Flange ball Bearing · General Electric GE90-76B, GE90-77B, GE90-85B and 1 more. Effective Jun 27, 1997
- [AD 2021-15-05](https://openairdocs.org/ad/2021-15-05) (historical): Engine Controls · General Electric GE90-110B1 and GE90-115B. Effective Sep 13, 2021
- [AD 2020-20-17](https://openairdocs.org/ad/2020-20-17) (historical): Engine Controls · General Electric GE90-110B1 and GE90-115B. Effective Oct 23, 2020
- [AD 2017-07-04](https://openairdocs.org/ad/2017-07-04) (historical): Compressor Section · General Electric GE90-110B1 and GE90-115B. Effective Apr 21, 2017
- [AD 2016-13-05](https://openairdocs.org/ad/2016-13-05) (historical): High-pressure compressor (HPC) stage 8-10 spool · General Electric GE90-76B, GE90-77B, GE90-85B and 2 more. Effective Jul 29, 2016
- [AD 2013-24-17](https://openairdocs.org/ad/2013-24-17) (historical): High pressure compressor (HPC) rotor stage 2-5 spools · General Electric GE90-110B1 and GE90-115B. Effective Dec 31, 2013
- [AD 2013-10-52](https://openairdocs.org/ad/2013-10-52) (historical): Transfer gearbox assemblies (TGBs) · General Electric GE90-110B1 and GE90-115B. Effective Jun 26, 2013
- [AD 2000-08-10](https://openairdocs.org/ad/2000-08-10) (historical): Life-limited Rotating Engine Parts · General Electric Aircraft Engines GE90-76B, GE90-77B, GE90-85B and 1 more. Effective Oct 23, 2000
- [AD 99-27-15](https://openairdocs.org/ad/99-27-15) (historical): Full Authority Digital Engine Control · General Electric Aircraft Engines GE90-76B, GE90-77B, GE90-85B and 17 more. Effective Jan 11, 2000
- [AD 99-08-17](https://openairdocs.org/ad/99-08-17) (historical): General Electric Aircraft Engines GE90-76B, GE90-77B, GE90-85B and 2 more. Effective May 13, 1999
- [AD 98-15-03](https://openairdocs.org/ad/98-15-03) (historical): High Pressure Compressor · General Electric Aircraft Engines GE90-76B, GE90-77B, GE90-85B and 17 more. Effective Jul 29, 1998
- [AD 2013-14-51](https://openairdocs.org/ad/2013-14-51) (historical): Failure of a transfer gearbox assembly radial gearshaft · General Electric GE90-110B1 and GE90-115B

## Registered aircraft by registry model (OpenAirDocs)

- [GE GE90-110B1](https://openairdocs.org/engine/ge-ge90-110b1): 91 aircraft (registry code 30046)
- [GE GE90-115B](https://openairdocs.org/engine/ge-ge90-115b): 51 aircraft (registry code 30048)
- [GE GE90-90B](https://openairdocs.org/engine/ge-ge90-90b): 23 aircraft (registry code 30036)
- [GE GE90 series](https://openairdocs.org/engine/ge-ge90-series): 1 aircraft (registry code 30201)
- [GE GE90-113B](https://openairdocs.org/engine/ge-ge90-113b): 0 aircraft (registry code 30047)
- [GE GE90-76B](https://openairdocs.org/engine/ge-ge90-76b): 0 aircraft (registry code 30042)
- [GE GE90-77B](https://openairdocs.org/engine/ge-ge90-77b): 0 aircraft (registry code 30043)
- [GE GE90-85B](https://openairdocs.org/engine/ge-ge90-85b): 0 aircraft (registry code 30044)
- [GE GE90-94B](https://openairdocs.org/engine/ge-ge90-94b): 0 aircraft (registry code 30045)

---
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